Weaponry firing devices



3, 1968 J. J. NASH 3,396,628

WEAPONRY FIRING DEVICES Filed July 5, 1965 5 Sheets-Sheet 1 INVENTORJOHN J. NASH ATTORNEY Aug. 13, 1968 J. J. NASH 3,396,628

WEAPONRY FIRING DEVICES Filed July 6, 1965 5 Sheets-Sheet 2 INVENTORJOHN J. NASH ATTORNEY 3, 1968 J. J. NASH 3,396,628

WEAPONRY FIRING DEVICES Filed July 6, 1965 4 5 Sheets-Sheet 3 INVENTORJOHN J. NASH ATTORNEY 3, 1968 J. J. NASH WEAPONRY FIRING DEVI CES 5 Sheets-Sheet 4 Filed July 6, 1965 INVENTOR JOHN J. NASH 13, 1968 J. J.NASH 3,396,628

WEAPONRY FIRING DEVICES Filed-July e, 1965 5 Sheets-Sheet 5 FIG. 20

INVENTOR JOHN J. NASH ATTORNEY United States Patent 3,396,628 WEAPONRYFIRING DEVICES John J. Nash, Ferguson, Mo., assignor to Alsco, Inc., St.Louis, Mo., a corporation of Delaware Filed July 6, 1965, Ser. No.469,406 23 Claims. (Cl. 891.814)

ABSTRACT OF THE DISCLOSURE A rocket launcher firing device including anintervalometer contained within a cylindrical housing sized forinsertion into one of the launcher tubes of either a 7 or 19 tube rocketlauncher. The intervalometer has two contact decks suitable for firing 6and 18 rockets respectively, and further includes a switch forisolating. the former deck from the source of electrical energy. Theswitch is activated by a pivotally mounted adapter plate which carries aplug-like connector element adapted forinsertion into a receptacle ineither one of the launchers. The disposition of the receptacle in the 7tube launcher is such that the adapted plate will be shifted to aposition where it holds the switch closed, while in the 19 tube launcherthe switch will be open. The intervalometer has a load position whereinno rocket will fire when the firing switch is closed and an arm positionwherein the first rocket will fire when the firing switch is closed. Thelauncher will fire the rockets in individual bursts or sequentialbursts.

This invention relates in general to certain new and useful improvementsin weaponry firing devices and, more particularly, to a switchingcontrol unit for firing airborne rocket launchers. 1

At the present time, the United States Air Force possesses a largequantity of disposable air-borne rocket launchers each comprising ingeneral a cylindrical housing having either seven or ninteen rockettu'bes axially disposed therein, each rocket tube being capable oflaunching one rocket. The launcher, which is fabricated from aninexpensive material such as pressed paper, mounts on the underside of afighter aircraft and is electrically connected to a switch in thecockpit thereof for firing. The launcher, being relatively inexpensive,is designed to be jettisoned after firing its complement of rockets.

Recently the United States Air Force has adopted a new weapons systemwhich appears similar to the launcher previously described but containsan internally mounted control means which can program the firing of therockets. This control means makes it possible for the pilot selectivelyto fire rockets one at a time, or in sequence, the latter usually beingreferred to as ripple firing. This programmed method of firing has beenfound to be so effective and desirable militarily that the former typeof rocket launchers have become obsolete.

It is therefore the primary object of the present invention to provide acontrol device which can be quickly and simply added to obsolete rocketlaunchers so as to modernize them and render them useable to meetcurrent military requirements.

It is another object of the present invention to provide a device of thetype stated which can be. optionally connected to and inserted withineither a seven or a ninteen tube rocket launcher.

It is a further object of the present invention to provide a device ofthe type stated which is rugged in construction and is economical tomanufacture.

With the above and other objects in view, my invention resides in thenovel features of form, construction, arrangement, and combination ofparts presently described and pointed out in the claims.

3,396,628 Patented Aug. 13, 1968 ice In the accompanying drawings:

. FIG. 1 is a front elevational view of a firing control deviceconstructed in accordance with and embodying the presentinvention, andshowing the adapter plate rotated so that the control deviceaccommodates a 19-tube rocket launcher.

. FIG. 2 is a side elevational view of a firing control deviceconstructed in accordance with and embodying the present invention.

FIG. 3 is a top plan view partially broken away and in .section of thefiring control device.

FIG. 4 is a front elevational view of the firing control device showingthe adapter plate rotated so as to permit the control device to fitwithin a 7-tube rocket launcher.

FIG. 5 is an exploded perspective view of the rocket launcherconstructed in accordance with and embodyin the present invention.

FIG. 6 is a sectional view taken along line 6-6 of FIG. 2.

FIG. 7 is a side elevational view of an intervalometer forming part ofthe present invention.

FIGS. 8, 9, 10, 11 and 12 are sectional views taken along lines 88, 99,1010, 11-11 and 12--12, respectively, of FIG. 7.

FIG. 13 is a sectional view taken along line 13-13 of FIG. 2.

FIG. 14 is a sectional view taken along line 14--14 of FIG. 1.

FIG. 15 is a sectional view taken along line 1515 of FIG. 4.

FIG. 16 is a perspective view of a 19-tube rocket launcher.

FIG. 17 is a rear elevational view of a l9-tube rocket launcher showingthe firing control device operatively mounted therein.

FIG. 18 is a perspective view of a 7-tube rocket launcher.

FIG. 19 is a rear elevational view of the 7-tube rocket launcher showingthe firing control device operatively mounted therein.

FIG. 20 is a schematic wiring diagram showing the firing control deviceconnected to the 19-tube rocket launch- FIG. 21 is a schematic wiringdiagram showing the firing circuit of the 7-tube rocket launcher.

Referring now in more detail and by reference characters to the drawingswhich illustrate a preferred embodiment of the present invention, Adesignates a firing control device comprising a substantially circularface or mounting plate 1 having an exterior face f and interior face iand being provided with apertures 2 and 3. Integrally formed on theperiphery of the mounting plate 1 are radially projecting tabs 4 and 5,respectively provided with circular apertures 6, 7, for purposespresently more fully appearing. In proximity to aperture 7 mountingplate 1 is cut away in the provision of notches 8 and 9, an elongatedaperture 10, and an arcuate aperture 11 concentric with the aperture 7.Near its periphery, mounting plate 1 is provided with a plurality ofspaced apertures 12 which accept the bolts 13. Finally, the mountingplate 1 is stamped or otherwise provided on its exterior face withvarious indicia as best illustrated in FIGS. 1 and 4. Disposed upon theinterior face of f of mounting plate 1, and held facewise in abutmenttherewith by the bolts 13 is a diametrally reduced circular dielectricbacking plate 14 having apertures 15, 16 which register with apertures2, 3, respectively, of the mounting plate 1. Backing-plate 14 is furtherprovided near its perimetral margin with equally spaced apertures 17which register with the apertures 12 and similarly accept the bolts 13.In the area in juxtaposition to and substantially defined by the arcuateaperture 11 and elongated aperture 10, the backing-plate 14 is cut awayin the provision of an aperture 18. Secured to backing-plate 14 byscrews 19 is a switch mount 20 which supports a micro-switch 21 so as topermit the roller 22 thereof to extend into aperture 18 above theinnermost end of arcuate aperture 11, all as best seen in FIGS. 14 and'15. conventionally mounted in apertures 2, 15 is a conventional singlethrow, double pole, toggle selector switch 23.

Rearwardly mounted on bolts 13 and held in spaced parallel relation tobacking plate 14 by spacer sleeves 24 and nuts 25, is circular supportplate 26 which is equivalent to backing plate 14 in diametral size andis provided with a circular aperture 27 having a notch 28 extendingradially therefrom. Operatively secured to support plate 26, by bolts 29and extending partially through aperture 27 is a rotarysolenoid-actuated stepping switch or socalled intervalometer 30.

Referring now to FIGS. 7 through 11, intervalometer 30 includes aratchet rotary solenoid 31 which is mechanically connected by means ofsupport rods 32 to an elongated end plate 33 and a spring biased detentmember 34 having two opposed forwardly projecting hemispheres 34 mountedon the face thereof. Also supported in spaced parallel relation betweenthe rotary solenoid 31 and the elongated end plate 33 are two stationaryannular dielectric wafers 35, 36 having annular faces F, f and f frespectively. Dielectric wafer 35 is provided on its face f with 9contacts c c c c c c c c and on its opposite face f with two contacts cIntermediate the contacts c c the wafer 35 is provided with spacedradially projecting terminals 37, 38. Similarly, the dielectric wafer 36is provided on its face f with six contacts e e e e 0 c and on its facef with one contact 0 all wired as schematically illustrated in FIG. 20.Extending concentrically through the dielectric wafers 35, 36, thespring biased detent member 34, and the elongated end plate 33 is arotor shaft 39 which is operatively connected at one end to rotarymechanism 40 of solenoid 31, and at its other end projects throughaperture 16 of backing plate 14 and aperture 2 of mounting plate 1 whereit is provided with a control knob 41. Operatively mounted on the rotorshaft 39 between the elongated end plate 33 and the spring biased detentmember 34 is a circular detent plate 42 having a plurality ofcircumferentially spaced apertures 43 which engage the forwardlyprojecting hemispheres 34 of spring biased member 34. Rigidly mounted onrotor shaft 39 for rotation within the confines of the apertures ofdielectric wafers 35, 36 are dielectric disks 44, 45, respectively,having opposed faces which are coplanar to the faces f f and f frespectively. One face of disk 44 is provided with an annular contactorplate 46 having a peripheral margin which is spaced inwardly from thecontacts c through 0 Radially projecting from the peripheral margin ofcontactor plate 46 is a contactor tab 47 which is in slidable abutmentwith the face f and is adapted to pass under and thereby contact thecontactors c through a but not the terminals 37, 38. On its oppositeface the disk 44 is provided with a contactor plate 48 having a notch 49formed in the periphery thereof, the notch 49 being sized to fit aroundthe contactor c but not the contact 0 For convenience of referencecontactor plate 48 and contact 0 are referred to as a safety contactorand a safety contact, respectively. Similarly, on one face the disk 45is provided with a contactor plate 50 having a radially projecting tab51 which slidably abuts against the face f and is adapted to contact thecontacts o through c". On its opposite face, the disk 45 is providedwith an annular contactor plate 52 which is in continuous contact withthe contact 0 The annular contactor plates 46, 48 and 50, 52 are securedto their respective disks 44, 45 and are electrically connectedtherethrough one to the other, by axially extending rivets 53. Thus, arotation of the rotor shaft 37 will bring the tab 47 into successivecontact with the contacts c through c The contact 0 will continuallybear against the face of annular contactor plate 48 as will thecontractor 0 except when aligned with notch 49 which occurs when tab 47is pointed generally toward terminals 37, 38. Concurrently with therotation of tab 47 through contacts c through c the tab 51 will bebrought into successive contact with the contacts '0 through "c". Thecontact 0 will continuously bear against the annular contactor plate 52,all for purposes presently'r'nore fully appearing.

Referring now to FIGS. 7 and 12, rotary mechanism 40 includes ratchetdisks 54, 54, the former being operatively attached to the rotarysolenoid 31, and adapted to oscillate therewith and the latter beingoperatively attached t0 the rotor shaft 39. Both ratchet disks 54, 54are provided with pawls 55, 55 which engage one another for advancementof the rotor shaft 39, but freely slip with respect to one another whenthe solenoid 31 returns to its initial position. Also fastenedoperatively to the rotary solenoid 31 for oscillation therewith and withthe ratchet disk 54 is a rocking cam 56 which momentarily opens anormally closed interrupter switch i which is secured to the terminals37, 38 "and breaks the circuit therebetween when the solenoid 31rotates. It should be noted that the rotary solenoid 31 is internallyspring biased and returns to its initial position after the rocking cam56 has opened. Additionally, bridging the terminals 37, 38 is theselector switch 23. Operatively suspended to the rear of support plate26 by its own lead wires which extend through notch 28 is a capacitor 57which is wired as schematically shown in FIG. 20 and is adapted tosuppress sparks. The various wires leading from intervalometer 30 aredisposed within a loom 58.

Operatively journaled to mounting plate 1 by rivet 59 which extendsthrough aperture 7 and for limited rotation thereon is adapter plate 60having its rear face relieved in the provision of channel 61 which,despite the position of relative rotation, is continually incommunication with elongated aperture 10 of mounting plate 1 andaperture 18 of backing plate 14. Secured to adapter plate 60' andextending through arcuate aperture 11 of mounting plate 1 is flat headrivet 62 which limits the relative angular movement between adapterplate 60 and mounting late 1 to the arc defined by arcuate aperture 11.As will be seen in FIGS. 14, 15, the roller 22 of micro-switch 21 ridesup onto the head of rivet 62 when the adapter plate 60 is rotatedcounterclockwise on mounting plate 1, that is to say, to the 7RDposition, whereby to close the microswitch 21. Adapter plate 60 isfurthermore provided with two apertures 63, 64, having loosely disposedtherein bayonet fasteners 65, 66 respectively, which are each providedwith pinned ends adapted to receive a conventional bayonet fitting, allfor purposes presently more fully appearing. Suitably secured to theback face of adapter plate 60 at one end and extending therefrom is atubular conduit 67 having a rectangular cross-section. At its other endthe tubular conduit 67 is provided with a conventional male connectorelement 68 having a plurality of connector pins extending therefrom.Loom 58 extends from intervalometer 30 through aperture 18 in backingplate 14, through elongated aperture 10 in mounting plate 1 thoughchannel 61 and into conduit 67 wherein the respective wires disposed inloom 58 are connected to the various pins of male connector element 68,as schematically illustrated in FIG. 20.

Intervalometer 30, micro-switch 21, support plate 26 and selector switch23, are all encased in a tubular housing 69 which is diametrally sizedinternally to slidably receive the support plate 26 and the backingplate 14. Provided for endwise closure of tubular housing 69 is circularend cap 70 which is held in spaced parallel relation to support plate 26and backing plate 14 by the spacer sleeves 71 and nuts 72. Forconvenience of reference mounting plate 1, backing plate 14, supportplate 26, end cap 70, bolts 13, and spacer sleeves 24 are referred toconjointly as a frame.

Firing control device A is operatively emplaced within a 19-tube rocketlauncher L as best seen in FIG. 17. It should be noted the maleconnector element 68 engages a mating receptacle element M having wiresconnected thereto which lead to the tail contacts F on the launcher L tothe power supply of the aircraft and to the firing switch s in thecockpit, all as schematically illustrated in FIG. 20. Tubular housing69, being slightly smaller in diametral size than launcher tube T fitsslidably therein whereupon the face 1 of mounting plate 1 comes intoabutment with the aft launcher bulkhead B to which it is secured byself-tapping screws 73 and lock fastener 66 which registers with andengages a bayonet fitting disposed therein. In such position adapterplate 60 will be rotated clockwise relative to mounting plate 1 and thenotch 8 will accommodate the shank of fastener 65. The head of rivet 62will be displaced to the outer end of arcuate aperture 11 and themicro-switch 21, of course, will be open.

Firing control device A is similarly received by a 7-tube launcher L asbest seen in FIG. 19. However, to fit within the 7-tube launcher L; theadapter plate 60 must be rotated fully counterclockwise with respect tomounting plate 1. Such a rotation places the shank of lock fastener 65in position to engage a bayonet fitting in the aft bulkhead B while thenotch 9 accommodates the shank of fastener 66. Such a position bringsthe head rivet 62 into contact with the roller 22 of micro-switch 21whereby to close the micro-switch 21.

The forwardly presented ends of launcher tubes T and T are each coveredwith a blast plate 74 to deflect the blast ejected by rockets inadjacent tubes as best seen in FIGS. 16 and 18.

To prepare the 19-tube rocket launcher L for firing it is firstoperatively secured to the underside of the air craft. Thereafterrockets are inserted in eighteen of the rocket tubes T The nineteenthtube T carries the firing control device A in the manner previouslydescribed herein. It should be noted that each of the rockets R includesa pair of contactors E which bear against corresponding electricalcontactors F disposed within each of the tubes T whereby to include theignition system of each of the rockets R within the firing circuit of,the launcherL One of the contactors F is grounded to the aircraft whilethe other is connected to the receptacle element M and thence to theintervalometer 30 as schematically illustrated in FIG. 20. It should befurther noted that the rockets R are connected in pairs through theconnector elements 68, M so that one electrical impulse Will fire tworockets R.

Knob 41 is set to L or the load or safety position in which notch 49 ofthe contactor plate 48 is disposed in surrounding relationship to thecontact a so as to preclude electrical current flow between the plate 48and contact 0 Advancing the knob 41 to A or the armed position bringscontactor plate 48 into electrical contact with contact c Now when thepilot presses the firing switch s a circuit to the rotary solenoid 31 isclosed, the circuit being traced as follows: from the electrical energysource of the aircraft, through the firing switch s through theconnector elements 68, M to the contact 0 through the contactor plate48, to the contact 0 to terminal 37 of the dielectric wafer 35 throughthe closed interrupter switch i to terminal 38, through solenoid 31 andthence to ground again through the connector elements 68 and M Once thesolenoid 31 is energized it advances one increment and thereby bringsthe tab 47 into contact with the contact 0 In this position, of course,a circuit to a pair of rockets R is established which, for purposes ofillustration can be traced as follows: from the electrical energy sourceof the aircraft through the firing switch .9, through the connectorelements 68, M to contact c and to the contactor plate 48, through therivets 53 into the contactor plate 46, through the tab 47 into thecontact c through the connector element 68 and M thence to thecontactors E of two rockets R, through the rockets R, and to groundwhich carries the current back to the power source. The next eightincremental advances of the tab 47 will successively complete thecircuit through two pair of rockets R until all sixteen of the remainingrockets R are expended. If the selector switch 23 is closed, that is tosay, is in the single position, the rotary solenoid 31 and ratchet disk54 will return to the initial position until the switch sis released.Thus, in the single position, the switch s must be depressed each timethe pilot desires to fire a salvo of two rockets R. However, when theselector switch 23 is opened, that is to say, is in the rippledposition, upon closure of switch s the solenoid 31 will advance and therocking cam 35 will open the interrupter switch i, thereby breaking thecircuit and allowing the solenoid 31 to return to its initial position.Of course, by the time the solenoid 31 has returned to its initialposition, the rocking cam 35 will have released the interrupter switch iwhereby to again close the circuit and advance the tab 47 an additionalincrement. Thus, the pilot by holding the firing switch s closed canignite all eighteen rockets R in closely spaced bursts of two.

Finally, it should be again noted that when each firing control device Ais emplaced in launcher L the microswitch 21 will be open, therebyinactivating the contacts c through c on the dielectric Wafer 36.

The 7-tube rocket launcher L is prepared for firing in a manner similarto launcher L Since one of the tubes T carries the firing control deviceA, only six tubes will be available for carrying rockets R. Moreover,since firing control device A mounts in launcher L7 with the microswitch21 closed, the circuit elements associated with dielectric wafer 36 willform a part of the firing circuit as best seen in FIGS. 20 and 21.

One advance of tab 47 past the armed position will bring it to 0 butsince no rocket R of the seven tube launcher L is connected to contact 0no rockets R will fire. It should be noted that the contactor tab 51 ofannular contactor plate 50 at this increment does not complete a circuitto a rocket R. The next incremental advance of rotor shaft 39 will bringtab 47 into contact with contact c and the tab 51 into contact Withcontact 0 which is connected by a lead wire to contact c and from thereto and through the connector elements 63, M to a single rocket R which,of course, will fire. In this regard, it should be noted that thecontactor tab 47 also completes circuits to the coatactors F in thelaunchers L but in effect electrically trails the tab 51 by oneincrement. In other words, when tab 51 completes a circuit and fires arocket R, the tab 47 will also complete a circuit to a rocket tube T butthe rocket R in such a tube T will have previously been fired by the tab51. Thus, the rockets R in launcher L, are fired one at a time by thesuccessive increment-a1 rotation of the tab 47 through the contacts ethrough Again, the operation of rotary solenoid 31 is controlled by thecircuit associated with the contactor plate 48, and the position ofselect-or switch 23 has the same effect, that is to say, when selectorswitch 23 is open the pilot must press and release the firing switch seach time he desires to fire a single rocket R. In other words, when thefiring switch s is pressed inwardly to close the circuit, the rotarysolenoid 31 will energize and will advance one step and Will remain inthis advanced position as long as it is energized. As has been aboveindicated, the single-step advance of the rotary solenoid 31 willcomplete a firing circuit to a single rocket, and once the rocket hasbeen fired it makes no difference if the pilot keeps his finger on thefiring switch s for a moment or two beyond the period actually requiredto fire the rocket because that particular rocket has already left thelauncher or is in the process of doing so and the firing circuitassociated with it no longer has any function during such particularcycle of firing. As soon as the pilot releases the firing switch s,after having closed it, the rotary solenoid 31 becomes deenergized andis pulled back to initial position by means of a spring-return which isa part of its mechanism, so that the rotary solenoid 31 thus becomescocked for the next stepwise advance of the contactor tab 51. Thus, ashas been previously pointed out, the rockets R will be fired, one at atime, by successive manipulations of the firing switch s at the will ofthe pilot.

If, on the other hand, the selector switch 23 has been shifted to theopen or so-called ripple fire position, the interrupter switch i willnot be bypassed and the rotary solenoid 31 will be automaticallyde-energized at the end of each stepwise advance even though the pilotholds the firing switch s closed, and the rockets R will therefore befired in closely spaced successive order. Since a complete salvo can befired in this manner within a period of less than 30 seconds, the pilotcan fire a complete salvo in the ripple fire sequence merely by holdingthe firing switch s closed for about a minute. It is possible, althoughnot considered to be desirable, for the pilot to close the firing switchs for a period of seconds or so and thereby fire a partial salvo andsubsequently fire the remainder of the salvo by a second manipulation ofthe firing switch s.

Thus, by the use of the firing control device A obsolete rocketlaunchers can be quickly provided with either single-fire or ripple firecapabilities. The firing control device A is actually a very small,compact unit which can be very readily shipped to remote supply depotsand therefore greatly simplifies the logistical problem of handlingobsolete rocket launchers. Moreover, the firing control device A can bevery quickly and easily inserted in either 7-tube or l9-tube rocketlaunchers without requiring any complicated machine tools or hand tools.In fact, the conversion can be effected within a matter of minutes byany ordnance mechanic without any great degree of special training orskill. Inasmuch as the mounting arrangement is positioned differentlyfor 7-tube or 19-tube rocket launchers and the change of positionautomatically consists of a change in firing circuitry, it is impossibleto make mistakes in the conversion procedure.

It should be understood that changes and modifications in the form,construction, arrangement and combination of several parts of the firingcontrol device A may be made and substituted for those herein shown anddescribed without departing from the nature and principle of myinvention.

Having thus described my invention, what I claim and desire to secure byLetters Patent is:

1. A firing control device for use with airborne rocket launchers havinga plurality of rocket tubes which are adapted to carry rockets, saidrocket launcher being provided with an electrical circuit including anelectrical receptacle, said firing control device comprising a faceplate, an intervalometer carried by said face plate, an adapter platerotatably journaled to said face plate and having a tubular conduitextending rearwardly therefrom substantially perpendicular to said faceplate, an electrical connector element operatively mounted on saidtubular conduit and being adapted for insertion into said electricalreceptacle, and a switch actuated by the adapter plate and associatedwith the intervalometer for adapting the intervalometer for use withrocket launchers of different rocket quantities.

2. A firing control device for use with airborne rocket launchers havinga plurality of rocket tubes which are adapted to carry rockets, saidrocket launcher being provided with an electrical circuit including anelectrical receptacle, said firing control device comprising a faceplate, an intervalometer carried by said face plate and sized to fitwithin a rocket tube, means for securing said face plate to the end ofthe rocket launcher so as to substantially cover the end of one rockettube, an adapter plate journaled to said face plate for rotation througha limited arc, a tubular conduit fastened at one end to said adapterplate and extending rearwardly therefrom substantially perpendicular tosaid face plate, said conduit being provided at its other end with anelectrical connector element, and a switch actuated by the adapter plateand associated with the intervalometer for adapting the intervalometerfor use with rocket launchers of different rocket quantities.

3. A firing control device for use with airborne rocket launchers havinga plurality of rocket tubes which are adapted to carry rockets, saidrocket launcher being provided with an electrical circuit including anelectrical receptacle, said firing control device comprising a faceplate, an intervalometer carried by said face plate and sized to fitwithin a rocket tube, means for securing said face plate to the end ofthe rocket launcher so as to substantially cover the end of one rockettube, an adapter plate journaled to said face plate for rotation througha limited arc from a first position to a second position, a tubularconduit fastened at one end to said adapter plate and extendingrearwardly therefrom substantially perpendicular to said face plate,said conduit being provided at its other end with an electricalconnector element, and a switch operatively associated with saidintervalometer, said switch being closed by said adapter plate when saidadapter plate is rotated to said second position.

4. A firing control device for use with airborne rocket launchers havinga plurality of rocket tubes which are adapted to carry rockets, saidrocket launchers being provided with an electrical circuit including anelectrical receptacle, said firing control device comprising a faceplate, an intervalometer carried by said face plate and sized to fitwithin a rocket tube, means for securing said face plate to the end ofthe rocket launcher so as to substantially cover the end of one rockettube, an adapter plate journaled to said face plate for rotation througha limited are, a tubular conduit fastened at one end to said adapterplate and extending rearwardly therefrom substantially perpendicular tosaid face plate, said conduit being provided at its other end with anelectrical connector element, an electrical circuit operativelyassociated with said intervalometer and electrical receptacle forconveying electrical firing impulses to the electrical circuit of thelauncher, and a switch in the circuit for adapting the intervalometerfor use with rocket launchers of different rocket quantities, saidswitch being actuated by the adapter plate.

5. A firing control device according to claim 2 in which theintervalometer includes a moving contactor means for completing anelectrical connection to a plurality of contacts in successive order,said contacts being electrically connected to said rocket.

6. A firing control device according to claim 5 having means operativelyassociated with said intervalometer for optionally causing said movingcontactor to continue movement until it has successively contacted allthe contacts or to move from one contact to the next one step at a time.

7. A firing control device according to claim 2 in which theintervalometer includes first and second moving contactor means forcompleting electrical connections to a plurality of first and secondcontacts in successive order.

8. A firing control device according to claim 6 wherein the switch is inthe circuit completed by said second contactor means whereby toelectrically isolate said second contactor means and said secondcontacts.

9. A firing control device for use with first and second airborne rocketlaunchers having a plurality of rocket tubes which are adapted to carryrockets, each of said rockets being adapated to ignite upon receipt ofan electrical impulse, said first rocket launcher being electricallywired to a first electrical receptacle so that a single impulse willignite at least two rockets, said second launcher being electricallywired to a second electrical receptacle so that a single impulse willfire a single rocket, said firing control device comprising a faceplate, a tubular housing projecting from said face plate and sized toslidably fit within said rocket tubes whereby said face plate abutsagainst the end of said rocket launcher, an intervalometer operativelydisposed within said tubular housing and being electrically connected toa source of electrical energy, an adapter plate journaled to said faceplate for rotation through a limited are from a first position to asecond position, a tubular conduit fastened to said adapter plate at oneend and extending therefrom in parallel spaced relation to said housing,said tubular conduit being provided at its other end with an electricalconnector element adapted to engage either said first or secondreceptacles, conductor means operatively associated with said connecterelement and said intervalometer whereby to electrically connect saidintervalometer and said rockets, said intervalometer being adapted tosuccessively close circuits to said rockets whereby to transferelectrical impulses thereto for firing the same, and a switch actuatedby the adapter plate and associated with the intervalometer forconverting the intervalometer circuitry so that it fires one or tworockets depending on the launcher in which the firing control device isinstalled.

10. A firing control device for use wit-h first and second airbornerocket launchers having a plurality of rocket tubes which are adapted tocarry rockets, each of said rockets being adapted to ignite upon receiptof an electrical impulse, said first rocket launcher being electricallywired to a first electrical receptacle so that a single impulse willignite at least two rockets, said second launcher being electricallywired to a second electrical receptacle so that a single impulse willfire a single rocket, said firing control device comprising a faceplate, a tubular housing projecting from said face plate and sized toslidably fit within said rocket tubes whereby said face plate abutsagainst the end of said rocket launcher, an intervalometer operativelydisposed within said tubular housing and being electrically connected toa source of electrical energy, said intervalometer including first andsecond contactor means for firing the rockets of said first and secondlaunchers, respectively, an adapter plate journaled to said face platefor rotation through a limited are from a first position to a secondposition, a switch operatively associ ated with said adapter plate forelectrically isolating said second contactor means from said source ofelectrical energy when said adapter plate is in said first position, atubular conduit fastened to said adapter plate at one end and extendingtherefrom in parallel spaced relation to said housing, said tubularconduit being provided at its other end with an electrical connectorelement adapted to engage said first receptacle when said adapter plateis in the first position and said second receptacle when said adapterplate is in the second position, and conductor means operativelyassociated with said connector element and said intervalometer wherebyto electrically connect said intervalometer and said rockets, saidintervalometer being adapted to successively close circuits to saidrockets whereby to transfer electrical impulses thereto for firing thesame.

II. A firing control device according to claim in which saidintervalometer is associated with selector means for optionally causingsaid intervalometer to fire all of its rockets in succesisve shortlyspaced bursts or one burst at a time.

12. A firing control device for use with first and second airbornerocket launchers having a plurality of rocket tubes which are adaptedtocarry rockets, each of said rockets being adapted to ignite upon receiptof an electrical impulse, said first rocket launcher being electricallywired to a first electrical receptacle so that a single impulse willignite at least two rockets, said second launcher being electricallywired to a second electrical receptacle so that a single impulse willfire a single rocket, said first and second electrical receptacles beingelectrically connected to an electrical energy source, firing meansremotely mounted from said launchers and being interposed between saidelectrical energy source and said receptacles, said firing controldevice comprising a face plate, a tubular housing projecting from saidface plate and sized to slidably fit within said rocket tubes whereby toallow said face plate to abut against the aft end of said launcher,means for securing said face plate to said launcher, an adapter platejournaled to said face plate for rotation through a limited are from afirst position to a second position, a tubular conduit fastened to saidadapter plate at one end and extending therefrom in parallel spacedrelation to said housing, said tubular conduit being provided at itsother end with an electrical connector element adapted to engage eithersaid first or second receptacle, an intervalometer housed within saidhousing and including first and second contactor means, conductor meansinterposed between said intervalometer and electrical connector elementwhereby to connect said intervalometer to said source of electricalenergy and said rockets, and a switch interposed between said electricalenergy source and said second contactor means and being operativelyassociated with said adapter plate for electrically isolating saidsecond contactor means from said electrical energy source when saidadapter plate is in said second position, said intervalometer beingadapted to transfer electrical impulses to said rockets through saidconductor means when said firing means is closed whereby to fire saidrockets.

13. A firing control device for use with first and second rocketlaunchers having a plurality of rocket tubes which are adapted to carryrockets, each of said rockets being adapted to ignite upon receipt of anelectrical impulse, said first rocket launcher being electrically wiredto a first electrical receptacle so that a single impule will ignite atleast two rockets, said second launcher being electrically wired to asecond electrical receptacle so that a single impulse will fire a singlerocket, said first and second electrical receptacles being electricallyconnected to an electrical energy source, firing means remotely mountedfrom said launchers and being interposed between said electrical energysource and said receptacles, said firing control device comprising aface plate, a tubular housing projecting from said face plate and sizedto slidably fit within said rocket tubes whereby to allow said faceplate to abut against the aft end of said launcher, means for securingsaid face plate to said launcher, an adapter plate journaled to saidface plate for rotation through a limited are from a first position to asecond position, a tubular conduit fastened to said adapter plate at oneend and extending therefrom in parallel spaced relation to said housing,said tubular conduit being provided at its outer end with an electricalconnector element adapted to engage either said first or secondreceptacle, an intervalometer housed within said housing and havingrotary means and first and second contactor means for firing the rocketsof said first and second launchers, respectively, said contactor meansincluding a plurality of spaced first contactors and a first rotarycontactor element secured to said rotary means and adapted to contactsaid first contactors one at a time, said second contactor meansincluding a plurality of spaced second contactors and a second rotaryelement adapted to contact said second contactors one at a time,conductor means interposed between said first and second rotary elementand said first and second electrical receptacles, whereby to transferelectrical impulses successively to said rockets when said rotary meansrotates, and a switch interposed between said electrical energy sourceand said second rotary element and operatively associated with saidadapter plate, said switch being open when said adapter plate is in saidsecond position.

14. A firing control device for use with first and second rocketlaunchers having a plurality of rocket tubes which are adapted to carryrockets, each of said rockets being adapted to ignite upon receipt of anelectrical impulse, said first rocket launcher being electrically wiredto a first electrical receptacle so that a single impulse will ignite atleast two rockets, said second launcher being electrically wired to asecond electrical receptacle so that a single impulse will fire a singlerocket, said first and second electrical receptacles being electricallyconnected to an electrical energy source, firing means remote ly mountedfrom said launchers and being interposed between said electrical energysource and said receptacles, said firing control device comprising aface plate, a tubular housing projecting from said face plate and sizedto slidably fit within said rocket tubes whereby to allow said faceplace to abut against the aft end of said launcher, means for securingsaid face plate to said launcher, an adapter plate journaled to saidface plate for rotation through a limited are from a first position to asecond posi ion, a tubular conduit fastened to said adapter plate at oneend and extending therefrom in parallel spaced relation to said housing,said tubular conduit being provided at its other end with an electricalconnector element adapted to engage either said first or secondreceptacle, an intervalometer housed within said housing and havingrotary means and first and second contactor means for firing the rocketsof said first and second launchers, respectively, said rotary meansbeing adapted for rotary incremental advancement when said firing meansis closed, said first contactor means including a plurality of spacedfirst contactors and a first rotary contactor element secured to saidrotary means and adapted to contact said first contactors, one at a timeon incremental advances, said second contactor means including aplurality of spaced second contactors and a second rotary elementadapted to contact said second contactors one at a time on incrementaladvances, conductor means interposed between said first and secondrotary elements and said first and second electrical receptacles,whereby to transfer electrical impulses successively to said rocketswhen said rotary means rotates, and a switch interposed between saidelectrical energy source and said second rotary element and beingoperatively associated with said adapter plate, said switch being openwhen said adapter plate is in said second position.

15. A firing control device according to claim 14 and having a selectormeans operatively associated with said intervalometer for optionallycausing said rotary means to advance in successive, closely spacedincrements once said firing means is closed whereby to ignite saidrockets of said first launcher in closely spaced salvos of two rocketseach and the rockets of said second launcher in closely spaced bursts.

16. For interchangeable use with first and second rocket launchersadapted to carry rockets which are ignited by electrical impulsesderived from a remote source of electrical energy; a firing controldevice comprising a frame, an intervalometer carried by the frame andconnected to the electrical energy source, the intervalometer includingfirst and second contactors which engage a plurality of spaced first andsecond contacts, respectively, conductor means for connecting thecontacts with the firing circuitry of the first or second rocketlaunchers, and a switch for optionally connecting or disconnecting thesecond contactor from the electrical energy source.

17. A firing device according to claim 16 and further characterized by aconnector element adapted to engage a mating connector element on therocket launchers and forming part of rocket firing circuitry thereof,the conductor means interconnecting the connector element and thecontacts.

18. A firing device according to claim 17 and further characterized byan adapter element shiftably mounted on the frame for movement betweenfirst and second positions, the adapter element carrying the connectorelement which registers with the mating coupler element on the firstlauncher when in the first position and registers with the matingcoupler element on the second launcher when in the second position, theswitch being actuated by the movement of the adapter element.

19. A firing control device for use on first and second Cir rocketlaunchers having a plurality of numerically different rocket tubes forcarrying rockets, each of which is adapted to ignite upon the receipt ofan electrical impulse, the first rocket launcher having a firstelectrical connector element disposed in a predetermined position withrespect to a preselected tube thereof and the second rocket launcherhaving a second electrical connector element which is disposed in adifferent position with respect to a preselected tube thereof, eachrocket launcher having electrical circuitry extending from theirrespective connector elements to the rockets carried thereby; saidfiring control device comprising a frame sized for insertion in therocket tubes, an intervalometer carried by the frame and being connectedto a source of electrical energy when the firing control device isinstalled in the launcher, the intervalometer including first and secondcontacts which successively engage a plurality of first and secondspaced contacts, an adapter element shiftably connected to the frame formovement from a first position to a second position with respect to theframe, a mating connector element on the adapter element, the matingconnector element being positioned so as to register with the firstconnector element on the first launcher when the adapter element is inits first position and the frame is inserted into the preselected tubeof the first launcher, the mating connector element being adapted toregister with the second connector element on the second launcher whenthe adapter element is in its second position and the frame is insertedin the preselected tube of the second launcher, conductor meansconnecting the contacts with the mating connector element whereby toelectrically connect the rockets with the intervalometer, and a switchactuated by the adapter element for disconnecting the second contactorfrom the electrical energy source when the adapter element is in thefirst position.

20. A firing device for rocket launchers adapted to carry and launchrockets which are ignited by means of electrical impulses, the firingdevice being energized by a remote electrical energy source and actuatedby a remote firing switch; said firing device comprising a frame adaptedto fit on the rocket launcher, an intervalometer mounted on the frameand being connected to the remote source of electrical energy, theintervalometer including a firing contactor and a plurality of spacedfiring contacts which lie in the path of the contactor firing, theintervalometer being adapted for incremental advancement sequentiallythrough a load position wherein it cannot be actuated when the firingswitch is closed, an arm position wherein it will advance one incrementwhen the firing switch is closed and thereby move the firing contactorinto electrical contact with the first of the spaced contactors firingcontacts, and a plurality of firing positions wherein the contactorengages a firing contact and completes an electrical circuit from theremote electrical energy source to a predetermined rocket so as toignite a predetermined rocket at each firing position, theintervalometer further including a safety contactor and a safety contactwhich electrically engages the safety contact except when theintervalometer is in the load position, the safety contactor and contactbeing connected in series between the electrical energy source andfiring contactor, and motive means for advancing the safety and firingcontactors, and being electrically connected to the safety contactor.

21. A firing device according to claim 20 and further characterized bymeans for optionally causing the motive means to advance the firingcontactors one increment at a time through each of the firing positionseach time the firing switch is closed or having it advance the firingcontactors incrementally in closely spaced intervals through all of thefiring positions once the firing switch is closed and held closed in thearm position.

22. A firing control device for use with first and second rocketlaunchers having a plurality of rocket tubes which rearwardly terminateat an aft bulkhead, the rockets being adapted for ignition upon receiptof electrical impulses derived from a remote energy source, the firstlauncher having a connector element disposed in a predetermined positionwith respect to one of its tubes, the second launcher having a connectorelement disposed in a ditferent predetermined position with respect toone of its tubes; said firing control device comprising a plate sized tofit over one of the rocket tubes and against the aft bulkhead, means forsecuring the plate to the aft bulkhead, a housing carried by the plateand sized to fit within the rocket tube carried by the plate, anintervalometer carried within the housing and connected to the remotesource of electrical energy, an adapter element shiftably mounted on theplate for movement from a first to a second position, connector meanscarried on the plate and being adapted to releasably engage theconnector element on the first launcher when the adapter element is inits first position and to releasably engage the connector element on thesecond launcher when the adapter plate is in its second position, and aswitch actuated by the adapter element and connected to theintervalometer for conditioning the intervalometer to the firingcircuitry of the first or second launchers.

23. A firing device for rocket launchers adapted to carry and launchrockets which are ignited by means of electrical impulses, the firingdevice being energized by a remote electrical energy source and actuatedby a remote firing switch; said firing device comprising a frame adaptedto fit on the rocket launcher and an intervalometer carried by theframe, the intervalometer including drive means adapted to advanceincrementally upon receipt of electrical impulses from the electricalenergy source, a firing contactor advanced incrementally b the drivemeans, a plurality of spaced firing contacts connected to the rocketsand lying in the path of the contactor, the firing contactor being inelectrical contact with the electrical energy source when it passes thefiring contacts so that the rockets are ignited in successive order, asafety contactor advanced incrementally with the firing contactor by thedrive means and having a dead portion, and a safety contact inelectrical engagement with the safety contactor except when it alignswith the dead portion, the safety contact and safety contactor beingconnected in series between the electrical energy source and drive meansso that the electric circuit to the drive means is interrupted when thesafety contact aligns with the dead portion whereby to define a loadposition, the location of the dead portion with respect to the firingcontactor being such that at least two incremental advances are requiredto move the contactor beyond the load position and onto the first firingcontact, the incremental advance immediately prior to the first contactplacin g the intervalometer in an arm position wherein the safetycontact and safety contactor are in electrical contact so that when thefiring switch is closed the firing contactor will advance to the firstfiring contact and ignite a rocket.

References Cited UNITED STATES PATENTS 2,421,893 6/1947 Lambert et al.89-1814 X 3,832,265 4/1958 Reid 89l.814 X 3,088,373 5/1963 Robert et al891.814

SAMUEL W. ENGLE, Primary Examiner.

